Determine the chamber pressure for a rocket engine if the thrust coeff – McqOptions

MCQOPTIONS

1.	Determine the chamber pressure for a rocket engine if the thrust coefficient is 1.8, the throat area is 0.2 m2 and the total thrust is 20000 N.
A.	61.33 kPa
B.	67.98 kPa
C.	45.67 kPa
D.	55.56 kPa
Answer» E.

Discussion

No Comment Found

Related MCQs

Afterburning can lead to ozone layer depletion.
At which of the following altitudes does the infrared emissions from the mixing zone of the rocket exhaust higher?
Which of the following is the mixing layer of a nozzle core flow?
If A is the pre-exponential factor, n is the temperature exponent, Ea is the activation energy, then the expression for forward rate constant according to Arrhenius law is ______
For strong emission signature of exhaust plumes, afterburning of fuel-rich gases is optimum for invisibility.
Which of the following correspond to the spectral bands of CO2 and H2O respectively in the IR signature of rocket exhaust plumes?
Determine the mass ratio (Burnout mass/ Initial mass) of a vehicle in a gravitation less space if its velocity is boosted from 800 m/s to 1600 m/s and the effective rocket exhaust velocity is 2000 m/s.
Determine the chamber pressure for a rocket engine if the thrust coefficient is 1.8, the throat area is 0.2 m2 and the total thrust is 20000 N.
What are the primary sources of radiation in a chemical rocket engine?
In which of these following altitudes does a rocket exhibit narrow pencil shaped exhaust plume?